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Optimization of blade arrangement in a randomly mistuned cascade using simulated annealingThis paper presents preliminary results of an investigation on mistuning of bladed-disk assemblies aimed at capturing the benefits of mistuning on stability, while at the same time, minimizing the adverse effects on response by solving the following problem: given a set of N turbine blades, each being a small random perturbation of the same nominal blade, determine the best arrangement of the N blades in a mistuned cascade with regard to aeroelastic response. In the studies reported here, mistuning of the blades is restricted to small differences in torsional stiffness. The large combinatorial optimization problem of seeking the best arrangement by blade exchanges is solved using a simulated annealing algorithm.
Document ID
19930066055
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Thompson, Edward A.
(NASA Lewis Research Center Cleveland, OH, United States)
Becus, Georges A.
(Cincinnati Univ. OH, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 93-2254
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit
Location: Monterey, CA
Country: United States
Start Date: June 28, 1993
End Date: June 30, 1993
Sponsors: ASEE, ASME, AIAA, SAE
Accession Number
93A50052
Funding Number(s)
CONTRACT_GRANT: NAG3-1173
Distribution Limits
Public
Copyright
Other

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